U.S. patent number 8,529,193 [Application Number 12/625,854] was granted by the patent office on 2013-09-10 for gas turbine engine components with improved film cooling.
This patent grant is currently assigned to Honeywell International Inc.. The grantee listed for this patent is Daniel Crites, Jong Liu, Malak Fouad Malak, Gopal Samy Muthiah, Dhinagaran Ramachandran, Balamurugan Srinivasan, Luis Tapia, Jyothishkumar Venkataramanan. Invention is credited to Daniel Crites, Jong Liu, Malak Fouad Malak, Gopal Samy Muthiah, Dhinagaran Ramachandran, Balamurugan Srinivasan, Luis Tapia, Jyothishkumar Venkataramanan.
United States Patent |
8,529,193 |
Venkataramanan , et
al. |
September 10, 2013 |
Gas turbine engine components with improved film cooling
Abstract
An engine component includes a body; and a plurality of cooling
holes formed in the body. At least one of the cooling holes has
cross-sectional shape with a first concave portion and a first
convex portion.
Inventors: |
Venkataramanan; Jyothishkumar
(Tamil Nadu, IN), Muthiah; Gopal Samy (Tamil Nadu,
IN), Ramachandran; Dhinagaran (Karnataka,
IN), Srinivasan; Balamurugan (Karnataka,
IN), Malak; Malak Fouad (Tempe, AZ), Liu; Jong
(Scottsdale, AZ), Tapia; Luis (Maricopa, AZ), Crites;
Daniel (Mesa, AZ) |
Applicant: |
Name |
City |
State |
Country |
Type |
Venkataramanan; Jyothishkumar
Muthiah; Gopal Samy
Ramachandran; Dhinagaran
Srinivasan; Balamurugan
Malak; Malak Fouad
Liu; Jong
Tapia; Luis
Crites; Daniel |
Tamil Nadu
Tamil Nadu
Karnataka
Karnataka
Tempe
Scottsdale
Maricopa
Mesa |
N/A
N/A
N/A
N/A
AZ
AZ
AZ
AZ |
IN
IN
IN
IN
US
US
US
US |
|
|
Assignee: |
Honeywell International Inc.
(Morristown, NJ)
|
Family
ID: |
43468498 |
Appl.
No.: |
12/625,854 |
Filed: |
November 25, 2009 |
Prior Publication Data
|
|
|
|
Document
Identifier |
Publication Date |
|
US 20110123312 A1 |
May 26, 2011 |
|
Current U.S.
Class: |
415/115;
416/97R |
Current CPC
Class: |
F01D
5/186 (20130101); Y02T 50/60 (20130101); Y02T
50/673 (20130101); F05D 2250/10 (20130101); F05D
2260/202 (20130101); Y02T 50/676 (20130101) |
Current International
Class: |
F03B
11/00 (20060101) |
Field of
Search: |
;415/115
;416/96R,97R,97A |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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|
|
|
|
|
|
0375175 |
|
Nov 1989 |
|
EP |
|
0924384 |
|
Jun 1999 |
|
EP |
|
0992653 |
|
Apr 2000 |
|
EP |
|
1609949 |
|
Dec 2005 |
|
EP |
|
1892375 |
|
Feb 2008 |
|
EP |
|
1942251 |
|
Jul 2008 |
|
EP |
|
1970628 |
|
Sep 2008 |
|
EP |
|
07332005 |
|
Dec 1995 |
|
JP |
|
2001012204 |
|
Jan 2001 |
|
JP |
|
2006307842 |
|
Nov 2006 |
|
JP |
|
Other References
Kusterer et al., Double-Jet Film-Cooling for Highly Efficient
Film-Cooling with Low Blowing Ratios, Proceedings of ASME Turbo
Expo 2008: Power for Land, Sea and Air GT2008, Jun. 9-13, 2008, pp.
1-12, Berlin, Germany, GT2008-50073. cited by applicant .
Wayne et al., High-Resolution Film Cooling Effectiveness Comparison
of Axial and Compound Angle Holes on the Suction Side of a Turbine
Vane, Transactions of the ASME, pp. 202-211, Copyright 2007 by
ASME. cited by applicant .
Lu et al., Turbine Blade Showerhead Film Cooling: Influence of Hole
Angle and Shaping, International Journal of Heat and Fluid Flow 28
(2007) pp. 922-931. cited by applicant .
Kim et al., Influence of Shaped Injection Holes on Turbine Blade
Leading Edge Film Cooling, International Journal of Heat and Mass
Transfer 47 (2004) pp. 245-256. cited by applicant .
Ramachandran et al., Turbine Engine Components, filed with the
USPTO on Jun. 24, 2009 and assigned U.S. Appl. No. 12/490,840.
cited by applicant .
EP Search Report, EP10187079.8-2321 dated Apr. 2, 2011. cited by
applicant .
Loh, Teck Seng; Srigrarom, Sutthiphong; Investigative Study of Heat
Transfer and Blades Cooling in the Gas Turbine, The
Smithsonian/NASA Astrophysics Data System; Modern Physics Letters
B, vol. 19, Issue 28-29, pp. 1611-1614 (2005). cited by applicant
.
Loh, Teck Seng; Srigrarom, Sutthiphong; Investigative Study of Heat
Transfer and Blades Cooling in the Gas Turbine, Modern Physics
Letters B, vol. 19, Issue 28-29, pp. 1611-1614 (2005). cited by
applicant .
Ronald S. Bunker; A Review of Shaped Hole Turbine Film-Cooling
Technology; Journal of Heat Transfer, Apr. 2005, vol. 127, Issue 4,
441 (13 pages). cited by applicant .
Shih, T. I.-P., Na, S.; Momentum-Preserving Shaped Holes for Film
Cooling; ASME Conference Proceedings, Year 2007, ASME Turbo Expo
2007: Power for Land, Sea, and Air (GT2007), May 14-17, 2007,
Montreal, Canada; vol. 4: Turbo Expo 2007, Parts A and B; Paper No.
GT2007-27600, pp. 1377-1382. cited by applicant .
Yiping Lu; Effect of Hole Configurations on Film Cooling From
Cylindrical Inclined Holes for the Application to Gas Turbine
Blades, A Dissertation, Submitted to the Graduate Faculty of the
Louisiana State University and Agricultural and Mechanical College,
Dec. 2007. cited by applicant .
Colban, W., Thole, K.; Influence of Hole Shape on the Performance
of a Turbine Vane Endwall Film-cooling Scheme, International
Journal of Heat and Fluid Flow 28 (2007), pp. 341-356. cited by
applicant .
Gartshore, I., Salcudean, M., Hassan, I.: Film Cooling Injection
Hole Geometry : Hole Shape Comparison for Compound Cooling
Orientation, American Institute of Aeronautics and Astronautics,
Reston, VA, 2001, vol. 39, No. 8, pp. 1493-1499. cited by applicant
.
Okita, Y., Nishiura, M.: Film Effectiveness Performance of an
Arrowhead-Shaped Film Cooling Hole Geometry, ASME Conference
Proceedings, ASME Turbo Expo 2006: Power for Land, Sea, and Air
(GT2006), May 8-11, 2006 , Barcelona, Spain, vol. 3: Heat Transfer,
Parts A and B, No. GT2006-90108, pp. 103-116. cited by applicant
.
Lu, Y., Allison, D., Ekkad, S. V.: Influence of Hole Angle and
Shaping on Leading Edge Showerhead Film Cooling, ASME Turbo Expo
2006: Power for Land, Sea, and Air (GT2006), May 8-11, 2006 ,
Barcelona, Spain, vol. 3: Heat Transfer, Parts A and B, No.
GT2006-90370 pp. 375-382. cited by applicant .
Heidmann et al., A Novel Antivortex Turbine Film-Cooling Hole
Concept, Journal of Turbomachinery, 2008 by ASME, Jul. 2008, vol.
130, pp. 031020-1-031020-9. cited by applicant .
Malak, F.M., et al.; Gas Turbine Engine Components With Film
Cooling Holes Having Cylindrical to Multi-Lobe Configurations, U.S.
Appl. No. 13/465,647, filed May 7, 2012. cited by
applicant.
|
Primary Examiner: White; Dwayne J
Attorney, Agent or Firm: Ingrassia Fisher & Lorenz,
P.C.
Claims
What is claimed is:
1. An engine component, comprising: a body; and a plurality of
cooling holes formed in the body, at least one of the cooling holes
having a cross-sectional shape with a first concave portion and a
first convex portion, wherein the cross-sectional shape has a
leading edge and a trailing edge, wherein the leading edge includes
the first convex portion transitioning into the first concave
portion, the first concave portion transitioning into a second
convex portion, and wherein the trailing edge includes a third
convex portion.
2. The engine component of claim 1, wherein the cross-sectional
shape is bean-shaped.
3. The engine component of claim 1, wherein the cross-sectional
shape is triad-shaped.
4. The engine component of claim 1, wherein the trailing edge
includes a second concave portion transitioning into the third
convex portion, the third convex portion transitioning into a third
concave portion.
5. The engine component of claim 1, wherein the cross-sectional
shape is reverse B-shaped.
6. The engine component of claim 1, wherein the cross-sectional
shape is dumbbell-shaped.
7. The engine component of claim 1, wherein the body is an airfoil
body.
8. The engine component of claim 1, wherein the body is a stator
vane body.
9. The engine component of claim 1, wherein the body is a rotor
blade body.
10. The engine component of claim 1, wherein the body is
hollow.
11. The engine component of claim 1, wherein the body has a suction
side and a pressure side.
12. An engine component, comprising: a body; and a plurality of
cooling holes formed in the body, at least one of the cooling holes
having a cross-sectional shape with a first concave portion and a
first convex portion, wherein the cross-sectional shape has a
leading edge and a trailing edge, wherein the leading edge includes
the first convex portion transitioning into the first concave
portion, the first concave portion transitioning into a second
convex portion, and wherein the trailing edge is generally
straight.
13. An engine component, comprising: a body; and a plurality of
cooling holes formed in the body, at least one of the cooling holes
having a cross-sectional shape with a first concave portion and a
first convex portion, wherein the cross-sectional shape has a
leading edge and a trailing edge, wherein the leading edge includes
the first convex portion transitioning into the first concave
portion, the first concave portion transitioning into a second
convex portion, and wherein the trailing edge includes a third
convex portion transitioning into a second concave portion, the
second concave portion transitioning into a fourth convex portion.
Description
TECHNICAL FIELD
The present invention generally relates to gas turbine engines, and
more particularly relates to air cooled components of gas turbine
engines, such as turbine and combustor components.
BACKGROUND
Gas turbine engines are generally used in a wide range of
applications, such as aircraft engines and auxiliary power units.
In a gas turbine engine, air is compressed in a compressor, and
mixed with fuel and ignited in a combustor to generate hot
combustion gases, which flow downstream into a turbine section. In
a typical configuration, the turbine section includes rows of
airfoils, such as stator vanes and rotor blades, disposed in an
alternating sequence along the axial length of a generally annular
hot gas flow path. The rotor blades are mounted at the periphery of
one or more rotor disks that are coupled in turn to a main engine
shaft. Hot combustion gases are delivered from the engine combustor
to the annular hot gas flow path, thus resulting in rotary driving
of the rotor disks to provide an engine output.
Due to the high temperatures in many gas turbine engine
applications, it is desirable to regulate the operating temperature
of certain engine components, particularly those within the
mainstream hot gas flow path, in order to prevent overheating and
potential mechanical issues attributable thereto. As such, it is
desirable to cool the rotor blades and stator vanes in order to
prevent damage and extend useful life. One mechanism for cooling
turbine airfoils is to duct cooling air through internal passages
and then vent the cooling air through holes formed in the airfoil.
The holes are typically formed uniformly along a line substantially
parallel to the leading edge of the airfoil and at selected
distances from the leading edge to provide a film of cooling air
over the convex side of the airfoil when the cooling air flows
therethrough during engine operation. Other rows of cooling holes
or an array of holes may be formed in the airfoil components
depending upon design constraints. Film cooling attempts to
maintain the airfoils at temperatures that are suitable for their
material and stress level.
A typical film cooling hole is a cylindrical aperture inclined
axially through one of the airfoil sides. In many conventional
engines, however, disadvantageous, relatively high cooling air
flows have been used to obtain satisfactory temperature control of
engine components.
Accordingly, it is desirable to provide a gas turbine engine with
improved film cooling. In addition, it is desirable to provide a
air-cooled turbine components with improved hole configurations.
Furthermore, other desirable features and characteristics of the
present invention will become apparent from the subsequent detailed
description of the invention and the appended claims, taken in
conjunction with the accompanying drawings and this background of
the invention.
BRIEF SUMMARY
In accordance with an exemplary embodiment, an engine component
includes a body; and a plurality of cooling holes formed in the
body. At least one of the cooling holes has a cross-sectional shape
with a first concave portion and a first convex portion.
In accordance with another exemplary embodiment, an engine
component, comprising includes a body; and a plurality of cooling
holes formed in the body. At least one of the cooling holes has a
triangle cross-sectional.
BRIEF DESCRIPTION OF THE DRAWINGS
The present invention will hereinafter be described in conjunction
with the following drawing figures, wherein like numerals denote
like elements, and wherein:
FIG. 1 is a partial, sectional elevation view illustrating a
portion of a turbine section of a gas turbine engine in accordance
with an exemplary embodiment;
FIG. 2 is a top cross-sectional view of an airfoil that can be
incorporated into the turbine section of FIG. 1 in accordance with
an exemplary embodiment;
FIGS. 3-7 are cross-sectional views of cooling holes that may be
incorporated into the airfoil of FIG. 2 in accordance with an
exemplary embodiment;
FIG. 8 is an exemplary perspective view of the cooling hole of FIG.
3; and
FIGS. 9-13 are cross-sectional views of the cooling holes of FIG.
3-7 illustrating construction techniques.
DETAILED DESCRIPTION
The following detailed description is merely exemplary in nature
and is not intended to limit the invention or the application and
uses of the invention. Furthermore, there is no intention to be
bound by any theory presented in the preceding background or the
following detailed description.
Broadly, exemplary embodiments discussed herein include gas turbine
engines with turbine components having improved film cooling. The
turbine components have a number of non-circular cooling holes. The
cooling holes may have, for example, both convex and concave
portions. For example, the cooling holes can have cross-sectional
shapes such as: bean-shaped, triad-shaped, reverse B-shaped,
dumbbell shaped, and/or triangle-shaped.
FIG. 1 is a partial sectional elevation view illustrating a portion
of a turbine section 100 of a gas turbine engine formed in
accordance with an exemplary embodiment. The turbine section 100
and gas turbine engine in general have an overall construction and
operation which is understood by persons skilled in the art. In
general terms, the turbine section 100 has a housing 102 with an
annular duct wall 104 that defines a mainstream hot gas flow path
106 for receiving mainstream gas flow 108 from an engine combustor
(not shown). The mainstream hot gas flow 108 flows past axially
spaced circumferential rows of airfoils 120, which include stator
vanes 122 and rotor blades 124 formed from suitable materials
capable of withstanding the high temperature environment within the
mainstream hot gas flow path 106.
The stator vanes 122 project radially outwardly from a
circumferential platform 126 to the annular duct wall 104. The
rotor blades 124 project radially outwardly from a circumferential
platform 128 that is adapted for appropriate connection to the
rotor disk (not shown) at the periphery thereof. The rotor disk is
generally positioned within the internal engine cavity and is
coupled to a main engine shaft for rotation therewith. As shown,
the rotor blade 124 and stator vane 122 may form one stage of a
multistage turbine. As such, multiple rows of the stator vanes 122
and the rotor blades 124 may be provided in the gas turbine section
100, with the rotor blades 124 and associated rotor disks being
rotatably driven by the hot gas flowing through the mainstream hot
gas flow path 106 for power extraction. A supply of cooling air,
typically obtained as a bleed flow from the compressor (not shown),
may pass through cooling holes in the airfoils 122, 124 to form a
surface cooling film. Although the cooling holes are discussed with
reference to turbine components, the cooling holes may also be
incorporated into other engine components, such as combustor
components. The cooling holes are discussed in greater detail
below.
FIG. 2 is a top cross-sectional view of an airfoil 200 that can be
incorporated into the turbine section 100 of FIG. 1 in accordance
with an exemplary embodiment. In general, the airfoil 200 may
correspond to the stator vane 122 or rotor blade 124 of FIG. 1, and
the cross-sectional view of FIG. 2 generally corresponds to a
horizontal cross-sectional view from the perspective of FIG. 1.
The airfoil 200 generally has a body 201 with a leading edge 202
and an opposite trailing edge 204. The airfoil 200 also includes a
pressure sidewall 206 that is generally concave and an opposite,
suction sidewall 208 that is generally convex and is spaced-apart
from the pressure sidewall 206. The pressure sidewall 206 and
suction sidewall 208 extend from leading edge 202 to trailing edge
204. The airfoil 200 has a hollow interior cavity 210 such that the
airfoil 200 has an inner surface 212 and an outer surface 214.
Airfoils 200 used in high performance gas turbine engines, such as
those used for aircraft propulsion, can be made from high heat and
high stress resistant aerospace alloys, such as nickel based
alloys, Rene 88, Inconel 718, single crystal materials, steels,
titanium alloys or the like.
As noted above, the airfoil 200 is subject to extremely high
temperatures because high velocity hot gases are ducted from the
combustor (not shown) onto the airfoil 200. If unaddressed, the
extreme heat may affect the useful life of an airfoil. As such,
film cooling is provided for the airfoil 200 to provide a cooling
film of fluid onto the surface of the airfoil 200, particularly in
the area of the leading edge 202 and areas immediately aft of the
leading edge 202. As noted above, cooling air is bled from the
compressor (not shown) or other source and passes into the interior
cavity 210 and through cooling holes 220 to the outer surface 214
of the airfoil 200. The cooling holes 220 are formed at locations
on the airfoil 200, particularly the convex side 206, concave side
208, and leading edge 202, to provide optimum cooling of the engine
component.
The cooling holes 220 may be formed in a selected pattern or array
to provide optimum cooling. The cooling holes 220 may be disposed
at any angle relative to the outer surface 206, such as about
20.degree. to about 40.degree., although the cooling holes 220 may
be oriented at lesser or greater angles. Computational fluid
dynamic (CFD) analysis can additionally be used optimize the
location and orientation of the cooling holes 220. The cooling
holes 220 may be formed by casting, abrasive water jet, Electron
Discharge Machining (EDM), laser drilling, or any suitable
process.
In general, the cooling holes 220 may be considered to have an
upstream portion 222 adjacent the inner surface 212 and a
downstream portion 224 adjacent the outer surface 214. The upstream
portion of each cooling hole 220, lying closer to the inner surface
212 is substantially cylindrical or circular and the downstream
portion lying closer to the outer surface 214 may have a
cross-sectional shape as discussed below with reference to FIGS.
3-13, particularly at the outer surface 214. The performance of the
airfoil 200 may be directly related to the ability to provide
uniform cooling of its surfaces with a limited amount of cooling
air. In particular, the size and shape of each hole 220 determine
the distribution of the air flow across the downstream surface.
Consequently, the cooling holes 220, particularly their
cross-sectional shapes, are important design considerations.
FIGS. 3-7 are cross-sectional views of cooling holes that may be
incorporated into the airfoil of FIG. 2 in accordance with an
exemplary embodiment. In reference to FIG. 2, the cross-sectional
views of FIGS. 3-7 correspond to view 224. FIG. 3 is a
cross-sectional view of a cooling hole 300, which may represent any
of the cooling holes 220 discussed in reference to FIG. 2, in
accordance with a first exemplary embodiment. The cooling hole 300
may be, for example, bean-shaped.
The cooling hole 300 may be considered to have an x-axis 380 and a
y-axis 390, as shown in FIG. 3. The cooling hole 300 may be
oriented in any suitable manner, and in one exemplary embodiment,
the cooling hole 300 is oriented such that the x-axis 380 is
parallel to the local streamlines of the combustion gases. In such
an embodiment, the cooling hole 300 has a leading edge 302 and a
trailing edge 352. The leading edge 302 generally has a convex
portion 304, a concave portion 306, and a convex portion 308. In
one exemplary embodiment, the convex portion 304 transitions
directly into the concave portion 306, which transitions directly
into the convex portion 308. The trailing edge 352 is generally
convex. As such, the cooling hole 300 generally has no straight
portions. The cooling hole 300 is generally symmetrical about the
x-axis 380 and asymmetrical about the y-axis 390.
FIG. 4 is a cross-sectional view of a cooling hole 400, which may
represent any of the cooling holes 220 discussed in reference to
FIG. 2, in accordance with a further exemplary embodiment. The
cooling hole 400 may be, for example, triad-shaped. In general, the
triad-shape of the cooling hole 400 may be formed by a grouping of
three overlapping circles.
The cooling hole 400 may be considered to have an x-axis 480 and a
y-axis 490, as shown in FIG. 4. The cooling hole 400 may be
oriented in any suitable manner, and in one exemplary embodiment,
the cooling hole 400 is oriented such that the x-axis 480 is
parallel to the local streamlines of the combustion gases. In such
an embodiment, the cooling hole 400 has a leading edge 402 and a
trailing edge 452. The leading edge 402 generally has a convex
portion 404, a concave portion 406, and a convex portion 408. In
one exemplary embodiment, the convex portion 404 transitions
directly into the concave portion 406, which transitions directly
into the convex portion 408. The trailing edge 452 generally has a
concave portion 454, a convex portion 456, and a concave portion
458. In one exemplary embodiment, the concave portion 454
transitions directly into the convex portion 456, which transitions
directly into the concave portion 458. As such, the cooling hole
400 generally has no straight portions and the concave portions
406, 454, 458 alternate with the convex portions 404, 408, 456. The
cooling hole 400 is generally symmetrical about the x-axis 480 and
asymmetrical about the y-axis 490.
FIG. 5 is a cross-sectional view of a cooling hole 500, which may
represent any of the cooling holes 220 discussed in reference to
FIG. 2, in accordance with a further exemplary embodiment. The
cooling hole 500 may have, for example, a reverse B-shape.
The cooling hole 500 may be considered to have an x-axis 580 and a
y-axis 590, as shown in FIG. 5. The cooling hole 500 may be
oriented in any suitable manner, and in one exemplary embodiment,
the cooling hole 500 is oriented such that the x-axis 580 is
parallel to the local streamlines of the combustion gases. In such
an embodiment, the cooling hole 500 has a leading edge 502 and a
trailing edge 552. The leading edge 502 generally has a convex
portion 504, a concave portion 506, and a convex portion 508. In
one exemplary embodiment, the convex portion 504 transitions
directly into the concave portion 506, which transitions directly
into the convex portion 508. The trailing edge 552 is generally
straight. The cooling hole 500 is generally symmetrical about the
x-axis 580 and asymmetrical about the y-axis 590.
FIG. 6 is a cross-sectional view of a cooling hole 600, which may
represent any of the cooling holes 220 discussed in reference to
FIG. 2, in accordance with a further exemplary embodiment. The
cooling hole 600 may be, for example, dumbbell-shaped.
The cooling hole 600 may be considered to have an x-axis 680 and a
y-axis 690, as shown in FIG. 6. The cooling hole 600 may be
oriented in any suitable manner, and in one exemplary embodiment,
the cooling hole 600 is oriented such that the x-axis 680 is
parallel to the local streamlines of the combustion gases. In such
an embodiment, the cooling hole 600 has a leading edge 602 and a
trailing edge 652. The leading edge 602 generally has a convex
portion 604, a concave portion 606, and a convex portion 608. In
one exemplary embodiment, the convex portion 604 transitions
directly into the concave portion 606, which transitions directly
into the convex portion 608. The trailing edge 652 generally has a
convex portion 654, a concave portion 656, and a convex portion
658. In one exemplary embodiment, the convex portion 654
transitions directly into the concave portion 656, which
transitions directly into the convex portion 658. As such, the
cooling hole 600 generally has no straight portions. The cooling
hole 600 is generally symmetrical about the y-axis 690 and
asymmetrical about the x-axis 680. In other embodiments, the
cooling hole 600 may generally symmetrical about the y-axis 690 and
symmetrical about the x-axis 680.
FIG. 7 is a cross-sectional view of a cooling hole 700, which may
represent any of the cooling holes 220 discussed in reference to
FIG. 2, in accordance with a further exemplary embodiment. The
cooling hole 700 may be, for example, triangle-shaped.
The cooling hole 700 may be considered to have an x-axis 780 and a
y-axis 790, as shown in FIG. 7. The cooling hole 700 may be
oriented in any suitable manner, and in one exemplary embodiment,
the cooling hole 700 is oriented such that the x-axis 780 is
parallel to the local streamlines of the combustion gases. In such
an embodiment, the cooling hole 700 has a leading edge 702 and a
trailing edge 752. The leading edge 702 is generally straight and
forms one of the sides 704 of the triangular shape. The trailing
edge 752 is formed by the other two sides 754, 756 of the
triangular shape. The sides 704, 754, 756 are generally straight
and are joined at corners 706, 760, 762, which may be formed by
curves or straight edge angles. The cooling hole 700 is generally
symmetrical about the x-axis 780 and asymmetrical about the y-axis
790.
In general, the cross-sectional shapes of the holes 220, 300, 400,
500, 600, 700 facilitate the distribution of the cooling air
substantially completely over the outer surface of the airfoil. In
particular, the cross-sectional shapes function as a diffuser to
reduce the velocity and increase static pressure of the cooling
airstreams exiting the holes and encourage cooling film
development. The holes 220, 300, 400, 500, 600, 700 additionally
increase the lateral spread distribution of the exiting airflows,
decrease peak velocities, and improve adiabatic effectiveness
across a number of blowing ratios. These airstreams are more
inclined to cling to the surface for improved cooling rather than
separate from the surface. This produces an enhanced cooling effect
at the surface. Consequently, exemplary embodiments promote the
service life of the airfoil (e.g., airfoils 122, 124, 200) as a
result of a more uniform cooling film at the external surfaces.
FIG. 8 is an exemplary perspective view of the cooling hole of FIG.
3. In general, FIG. 8 illustrates an upstream end 802, a downstream
end 804, and a transition portion 806 that transitions between the
upstream end 802 and the downstream end 804. As noted above, the
upstream end 802 is typically circular or cylindrical with a
diameter d. In other embodiments, the upstream end 802 is oval with
a minor diameter and a major diameter. As also noted above, the
downstream end 804 in FIG. 8 corresponds to the bean-shape of the
cooling hole 300 of FIG. 3. Additionally, the cooling holes 400,
500, 600, 700, 800 similarly have circular or oval upstream ends
that transition into the downstream ends discussed above with
reference to FIGS. 4-7.
FIGS. 9-13 are cross-sectional views of the cooling holes of FIG.
3-7 illustrating construction techniques. The techniques and
dimensions discussed with reference to FIGS. 9-13 are exemplary and
other techniques or dimensions may be provided.
For example, the cooling hole 300 of FIG. 9 generally corresponds
to the cooling hole 300 of FIG. 3. During construction, two
identical construction circles 902, 904 are formed and joined at a
tangent 906 that generally corresponds to the final center of the
cooling hole 300. In one exemplary embodiment, the construction
circles 902, 904 have diameters 912, 914 proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 300. In one exemplary embodiment, the diameters 912, 914 may
be, for example, about 1.6 d to about 1.7 d, particularly about
1.65 d. Next, a construction circle 908 is formed and joined at
tangents to construction circles 902, 904. In one exemplary
embodiment, the construction circle 908 has a diameter 918
proportionate to the diameter d (e.g., d of FIG. 8) of the upstream
end of the cooling hole 300. If the upstream portion is an oval,
diameter d may correspond to the minor diameter, although diameter
d may also correspond to the major diameter. In one exemplary
embodiment, the diameter 918 may be, for example, about 3.1 d to
about 3.2 d, particularly about 3.15 d. A distance 920 from the
edge of construction circle 908 to the center of construction
circles 902, 904 may be defined as L. In a next step, a curve 930
extending through points 922, 924, 926 is formed. Points 922, 926
correspond to edges of construction circles 902, 904 opposite
tangent 906. Point 924 is generally formed on a line 929 formed
through the tangent 906 and the diameter 918 of construction circle
908. Point 924 is formed at a distance 928 that is proportionate to
distance 920. For example, the distance 928 may be, for example,
about 2.5 L. The final shape (indicated by solid lines) of the
cooling hole 300 is formed by portions of construction circles 902,
904, 908 and curve 930.
FIG. 10 illustrates a cooling hole 400 that generally corresponds
to the cooling hole 400 of FIG. 4. During construction, two
identical construction circles 1002, 1004 are formed and joined at
a tangent 1006 that generally corresponds to the final center of
the cooling hole 400. In one exemplary embodiment, the construction
circles 1002, 1004 have diameters 1012, 1014 proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 400. If the upstream portion is an oval, diameter d may
correspond to the minor diameter, although diameter d may also
correspond to the major diameter. In one exemplary embodiment, the
diameters 1012, 1014 may be, for example, about 1.5 d to about 1.6
d, particularly about 1.53 d. Next, construction circles 1020, 1022
are formed and joined at tangents to construction circles 1002,
1004. In one exemplary embodiment, the construction circles 1020,
1022 have diameters 1024, 1026 proportionate to the diameter d
(e.g., d of FIG. 8) of the upstream end of the cooling hole 400. In
one exemplary embodiment, the diameters 1024, 1026 may be, for
example, about 2 d. As such, the construction circles 1020, 1022
may be separated by a distance 1028. The distance 1028 may be, for
example, about 1.1 d to about 1.2 d, particularly about 1.15 d. The
final shape (indicated by solid lines) of the cooling hole 400 is
formed by portions of construction circles 1002, 1004, 1020,
1022.
FIG. 11 illustrates a cooling hole 500 that generally corresponds
to the cooling hole 500 of FIG. 5. During construction, two
identical construction circles 1102, 1104 are formed and joined at
a tangent 1106 that generally corresponds to the final center of
the cooling hole 500. In one exemplary embodiment, the construction
circles 1102, 1104 have diameters 1112, 1114 proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 500. If the upstream portion is an oval, diameter d may
correspond to the minor diameter, although diameter d may also
correspond to the major diameter. In one exemplary embodiment, the
diameters 1112, 1114 may be, for example, approximately equal to
the diameter d. Next, construction circle 1120 is formed and joined
at tangents to construction circles 1102, 1104. In one exemplary
embodiment, the construction circle 1120 has a diameter 1122
proportionate to the diameter d (e.g., d of FIG. 8) of the upstream
end of the cooling hole 500. In one exemplary embodiment, the
diameter 1122 may be, for example, about 1 d to about 1.2 d,
particularly about 1.1 d. A line 1130 tangent to both construction
circles 1102, 1104 is formed, and a distance 1132 from line 1130 to
construction circle 1120 may be, for example, about 0.85 d. The
final shape (indicated by solid lines) of the cooling hole 500 is
formed by portions of construction circles 1102, 1104, 1120 and
line 1130.
FIG. 12 illustrates a cooling hole 600 that generally corresponds
to the cooling hole 600 of FIG. 6. During construction, two
identical construction circles 1202, 1204 are formed and joined at
a tangent 1208 that generally corresponds to the final center of
the cooling hole 600. In one exemplary embodiment, the construction
circles 1202, 1204 have diameters 1212, 1214 proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 600. If the upstream portion is an oval, diameter d may
correspond to the minor diameter, although diameter d may also
correspond to the major diameter. In one exemplary embodiment, the
diameters 1212, 1214 may be, for example, approximately equal to
diameter d. Next, a construction circle 1206 is formed and is
tangent to tangent 1208, as shown. In one exemplary embodiment, the
construction circle 1206 has a diameter 1216 proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 600. In one exemplary embodiment, the diameter 1216 may be,
for example, approximately equal to diameter d. As such, a distance
1220 from the tangent 1208 to the opposite edge of construction
circle 1206 may be, for example, approximately equal to diameter d.
A construction circle 1222 with a diameter 1232 is formed and
arranged tangent to construction circles 1202, 1204. In one
exemplary embodiment, the diameter 1232 is proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 600. In one exemplary embodiment, the diameter 1232 may be,
for example, approximately equal to diameter d to about 1.2 d,
particularly about 1.1 d. A construction circle 1224 with a
diameter 1234 is formed and arranged tangent to construction
circles 1202, 1206. In one exemplary embodiment, the diameter 1234
is proportionate to the diameter d (e.g., d of FIG. 8) of the
upstream end of the cooling hole 600. In one exemplary embodiment,
the diameter 1234 may be, for example, approximately 2 d.
Similarly, a construction circle 1226 with a diameter 1236 is
formed and arranged tangent to construction circles 1204, 1206. In
one exemplary embodiment, the diameter 1236 is proportionate to the
diameter d (e.g., d of FIG. 8) of the upstream end of the cooling
hole 600. In one exemplary embodiment, the diameter 1236 may be,
for example, approximately 2 d. The final shape (indicated by solid
lines) of the cooling hole 600 is formed by portions of
construction circles 1202, 1204, 1206, 1222, 1224, 1226.
FIG. 13 illustrates a cooling hole 700 that generally corresponds
to the cooling hole 700 of FIG. 7. During construction, three
generally straight sides 704, 754, 756 are formed. The sides 704,
754, 756 may have a length proportionate to the diameter d (e.g., d
of FIG. 8) of the upstream end of the cooling hole 700. If the
upstream portion is an oval, diameter d may correspond to the minor
diameter, although diameter d may also correspond to the major
diameter. In one exemplary embodiment, the sides 704, 754, 756 may
have a length, for example, about 1.3 d to about 1.5 d,
particularly about 1.4 d. In general, corners 706, 760, 762 may be
formed with a radius of curvature of about 0.12 d. In other words,
the corners 706, 760, 762 may be formed with construction circles
having an exemplary diameter of about 0.24 d, such as shown by
construction circle 708. The final shape (indicated by solid lines)
of the cooling hole 700 is formed by sides 704, 754, 756 and
corners 706, 760, 762.
Exemplary embodiments disclosed herein are generally applicable to
air-cooled components, and particularly those that are to be
protected from a thermally and chemically hostile environment.
Notable examples of such components include the high and low
pressure turbine nozzles and blades, shrouds, combustor liners and
augmentor hardware of gas turbine engines. Additionally, the
cooling holes discussed above may be incorporated into turbine
components. The advantages are particularly applicable to gas
turbine engine components that employ internal cooling to maintain
the service temperature of the component at an acceptable level
while operating in a thermally hostile environment.
While at least one exemplary embodiment has been presented in the
foregoing detailed description of the invention, it should be
appreciated that a vast number of variations exist. It should also
be appreciated that the exemplary embodiment or exemplary
embodiments are only examples, and are not intended to limit the
scope, applicability, or configuration of the invention in any way.
Rather, the foregoing detailed description will provide those
skilled in the art with a convenient road map for implementing an
exemplary embodiment of the invention. It being understood that
various changes may be made in the function and arrangement of
elements described in an exemplary embodiment without departing
from the scope of the invention as set forth in the appended
claims.
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